US3403842A - Stall prevention in axial flow compressors - Google Patents

Stall prevention in axial flow compressors Download PDF

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Publication number
US3403842A
US3403842A US606757A US60675767A US3403842A US 3403842 A US3403842 A US 3403842A US 606757 A US606757 A US 606757A US 60675767 A US60675767 A US 60675767A US 3403842 A US3403842 A US 3403842A
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US
United States
Prior art keywords
compressor
stall
pressure
probes
stage
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
US606757A
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English (en)
Inventor
Jean A Roche
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Co
Original Assignee
General Electric Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Priority to US606757A priority Critical patent/US3403842A/en
Priority to GB39136/67A priority patent/GB1167387A/en
Priority to BE704511D priority patent/BE704511A/xx
Priority to DE19671628269 priority patent/DE1628269A1/de
Application granted granted Critical
Publication of US3403842A publication Critical patent/US3403842A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0246—Surge control by varying geometry within the pumps, e.g. by adjusting vanes
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T137/00—Fluid handling
    • Y10T137/206—Flow affected by fluid contact, energy field or coanda effect [e.g., pure fluid device or system]
    • Y10T137/2065—Responsive to condition external of system
    • Y10T137/2071—And causing change or correction of sensed condition
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T137/00—Fluid handling
    • Y10T137/206—Flow affected by fluid contact, energy field or coanda effect [e.g., pure fluid device or system]
    • Y10T137/212—System comprising plural fluidic devices or stages
    • Y10T137/2125—Plural power inputs [e.g., parallel inputs]
    • Y10T137/2147—To cascaded plural devices

Definitions

  • incipient stall conditions occur in a segment of rotor blades of a given stage. If corrective action is not taken, or if the cause of the original stall is not removed, this pocket stall condition will spread to the entire stage and then other stages of the compressor eventually causing a gross" stall and rendering the compressor essentially inoperative.
  • a pocket stall may occur in a rotor or stator row and may be stationary or may rotate about the compressor axis. The angular location of a stationary pocket stall is usually predictable and related to the location of supporting frame structure between the outer casing and the support for the bearing journaling the rotor 16.
  • pressure sensors in the form of probes 40, 42 are disposed between the stators 22 of that stage.
  • the probes 4t), 42 are so spaced that under normal operating conditions essentially the same total air stream pressure is effective on each probe.
  • a conduit 44 is pressurized from the discharge of the compressor 12.
  • the conduit 44 is connected to probes 46 and 48 through pressure dropping orifices 50. Air is thus continuously discharged from the probes and 42 into the air stream of the compressor.
  • the pressure in the conduits 46 and 48 reflects the back pressure of the air stream on the probes.
  • the pressures of these conduits provides inputs to a fluid amplifier 52 which has a power stream nozzle 54 connected to the high pressure conduit 44 and discharges a power stream towards output receivers 56 and 58, as well as a central receiver 60, which is vented to atmosphere.
  • conduits 46 and 58 The sensed pressure of conduits 46 and 58 is connected to control ports 62, 64 on opposite sides of the power stream discharge from the nozzle 54.
  • the receivers 56 and 58 are connected to a common passageway or conduit 66, one end of which is connected to a fluid amplifier 68 and the other end of which is vented to atmosphere through an orifice 70.
  • the fluid amplifier 68 comprises a power nozzle 72 which is also connected to high pressure conduit 34. Control ports 74, 76 are disposed on opposite sides of the power stream, and receivers 78, 80 are downstream thereof.
  • the receiver 80 is connected by a conduit 82 to a transducer 84 which, for example, might be of the piezoelectric type to provide an electrical control signal transmitted by line 86 to a control valve 88 for regulating flow of pressurized fluid through the conduits 44, 46, leading to the actuator 32.
  • control port 74 of fluid amplifier 68 will likewise be at ambient pressure, as will control port 76 which is directly ported to ambient pressure. Under these circumstances, the power stream from nozzle 72 will be discharged through receiver 73 and vented to atmosphere.
  • Probes 40, 42 are also provided in the last compression stage of the compressor 12. Since the pressure in the last stage is essentially the same as at the compressor discharge, lines 46', 48' connect these probes directly to a fluid amplifier 52 which may be of identical construction with the amplifier 52 (component portions are not specifically designated by reference characteristics) to provide a stall warning signal in a conduit 66.
  • This stall warning signal may be amplified by fluid amplifier 68 which is identical with the fluid amplifier 68 and provides an amplified stall warning signal in conduit 82', and likewise provides a signal from transducer 84 to control valve 88.
  • the illustrated probes 40', 42' illustrate the fact that stall conditions can originate in any of the various stages of a compressor. It is, therefore, contemplated that probes would be provided in any stage where experience or analysis indicates stall may originate.
  • the stall warning signals as shown, may be fed to a single control means for reducing the load on the compressor to eliminate the stall conditions before a gross stall occurs.
  • the probes 40', 42 also illustrate that an angular spacing of (as in the case of probes 40, 42) is not required, but it would be pointed out that a minimum spacing is approximately 30.
  • the described system also adapts itself to the introduction of a false stall warning signal, as by putting a pressure input signal to one of the conduits 46 or 48 to purposely reset the stator vanes where a condition of hot gas ingestion into the compressor is to be encountered, as in operation of a thrust reverser or a firing of rockets from a plane propelled by the engine.
  • an axial flow compressor having at least one 3.
  • a plurality of stages of compression and comprising a P f p f Sensors angulaflif pacedfelative to rotor having axially spaced, circumferential rows of WHIP?sslon stage and Pwvldlng flnld Pmssllre blades and alternating rows of stator blades, each adjaa g si zl a inpfi e ha g a nozzle from which a power cent row of rotor and stator blades forming a compressor stage, the stators of at least the initial compressor stages stream is directed, bein ivotal b t 1 f h a pair of control ports opening on opposite sides of fi on axes ra 1a 0 t e compressor rotor the power stream, a pair of output receivers downstream of said control the means for reducing the aerodynamic
  • a second fluid amplifier having a nozzle UNITED STATES PATENTS from which a power stream is discharge 2,390,043 12 1945 Borden 230 1 5 a control port on one side of said power stream and 2 455 292 11/1948 Borden 230 115 receiver means dOWIlStl'fiflIfl 0f Said Co trol P 04 19 Ta 230 115 said interconnecting passageway being connec ed to 3327933 6/1967, fi
  • said one control port of said second amplifier to provide an amplified stall warning signal from said receiver means.

Landscapes

  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Geometry (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Positive-Displacement Air Blowers (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Turbines (AREA)
US606757A 1967-01-03 1967-01-03 Stall prevention in axial flow compressors Expired - Lifetime US3403842A (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
US606757A US3403842A (en) 1967-01-03 1967-01-03 Stall prevention in axial flow compressors
GB39136/67A GB1167387A (en) 1967-01-03 1967-08-25 Improvements in Axial Flow Compressors
BE704511D BE704511A (fr) 1967-01-03 1967-09-29
DE19671628269 DE1628269A1 (de) 1967-01-03 1967-10-02 Einrichtung zum Verhindern des Abreissens der Stroemung in einem Axialverdichter

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US606757A US3403842A (en) 1967-01-03 1967-01-03 Stall prevention in axial flow compressors

Publications (1)

Publication Number Publication Date
US3403842A true US3403842A (en) 1968-10-01

Family

ID=24429325

Family Applications (1)

Application Number Title Priority Date Filing Date
US606757A Expired - Lifetime US3403842A (en) 1967-01-03 1967-01-03 Stall prevention in axial flow compressors

Country Status (4)

Country Link
US (1) US3403842A (fr)
BE (1) BE704511A (fr)
DE (1) DE1628269A1 (fr)
GB (1) GB1167387A (fr)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3514212A (en) * 1968-06-11 1970-05-26 Us Air Force Incipient stall sensor
US3566900A (en) * 1969-03-03 1971-03-02 Avco Corp Fuel control system and viscosity sensor used therewith
US3677000A (en) * 1970-04-27 1972-07-18 Faulkner C Thomson System for the detection and control of compressor stall
DE2909825A1 (de) * 1978-03-14 1979-09-20 Rolls Royce Steuersystem fuer einen mehrstufigen axialstroemungskompressor eines gasturbinentriebwerks
US20060101826A1 (en) * 2004-11-12 2006-05-18 Dan Martis System and method for controlling the working line position in a gas turbine engine compressor
US20090173077A1 (en) * 2006-09-13 2009-07-09 Aerojet-General Corporation Nozzle with Temperature-Responsive Throat Diameter
CN110418881A (zh) * 2017-03-07 2019-11-05 赛峰飞机发动机公司 用于检测有助于发生泵送的条件以保护飞行器涡轮发动机的压缩机的方法和设备

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CS175129B1 (fr) * 1975-02-11 1977-04-29
DE2645895C2 (de) * 1976-02-10 1986-06-26 Nordisk Ventilator Co. A/S, Naestved Vorrichtung zur Erkennung des Arbeitens von Axialgebläsen im Abreißgebiet
GB2208894A (en) * 1987-08-18 1989-04-19 Rolls Royce Plc Gas turbine engine compressor stall recovery

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2390043A (en) * 1944-04-13 1945-12-04 Chrysler Corp Control apparatus
US2455292A (en) * 1944-04-13 1948-11-30 Chrysler Corp Control apparatus
US3248043A (en) * 1963-06-25 1966-04-26 Bendix Corp Fluid pulse surge control indicator
US3327933A (en) * 1964-08-07 1967-06-27 Bbc Brown Boveri & Cie Apparatus for regulating a turbocompressor

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2390043A (en) * 1944-04-13 1945-12-04 Chrysler Corp Control apparatus
US2455292A (en) * 1944-04-13 1948-11-30 Chrysler Corp Control apparatus
US3248043A (en) * 1963-06-25 1966-04-26 Bendix Corp Fluid pulse surge control indicator
US3327933A (en) * 1964-08-07 1967-06-27 Bbc Brown Boveri & Cie Apparatus for regulating a turbocompressor

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3514212A (en) * 1968-06-11 1970-05-26 Us Air Force Incipient stall sensor
US3566900A (en) * 1969-03-03 1971-03-02 Avco Corp Fuel control system and viscosity sensor used therewith
US3677000A (en) * 1970-04-27 1972-07-18 Faulkner C Thomson System for the detection and control of compressor stall
DE2909825A1 (de) * 1978-03-14 1979-09-20 Rolls Royce Steuersystem fuer einen mehrstufigen axialstroemungskompressor eines gasturbinentriebwerks
US4252498A (en) * 1978-03-14 1981-02-24 Rolls-Royce Limited Control systems for multi-stage axial flow compressors
US20060101826A1 (en) * 2004-11-12 2006-05-18 Dan Martis System and method for controlling the working line position in a gas turbine engine compressor
US7762084B2 (en) * 2004-11-12 2010-07-27 Rolls-Royce Canada, Ltd. System and method for controlling the working line position in a gas turbine engine compressor
US20090173077A1 (en) * 2006-09-13 2009-07-09 Aerojet-General Corporation Nozzle with Temperature-Responsive Throat Diameter
US7762078B2 (en) * 2006-09-13 2010-07-27 Aerojet-General Corporation Nozzle with temperature-responsive throat diameter
CN110418881A (zh) * 2017-03-07 2019-11-05 赛峰飞机发动机公司 用于检测有助于发生泵送的条件以保护飞行器涡轮发动机的压缩机的方法和设备

Also Published As

Publication number Publication date
GB1167387A (en) 1969-10-15
BE704511A (fr) 1968-02-01
DE1628269A1 (de) 1971-04-29

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